Issued: June 27, 2011 226-27-072

Page 1 of 8

SERVICE BULLETIN

SA226 SERIES

FLIGHT CONTROLS

Flight Control Cable Replacement

1. PLANNING INFORMATION

A. Effectivity:

SA226-T, S/N T265, T267

SA226-T(B), S/N T(B)348

SA226-TC, S/N TC277

SA226-AT, S/N AT071, AT072, AT073

B. Reason:

Safety improvement to prevent premature cable failure. Additional stress is exerted on

primary flight control cables that have been re-routed from standard configuration to

accommodate belly-mounted camera installations.

C. Description:

Replace all elevator, rudder, aileron, and aileron-to-rudder interconnect primary control cables as identified in step 2.C., or 2.D., or 2.E. every 3500 hours TIS. The existing

10000 hour time in service (TIS) life limit for all other cables per AD 87-02-02 remains

in effect.

D. Compliance:

Highly Recommended

A reduced life limit per Step 2.B. is placed against particular control cables.

M7 Aerospace recommends a one time check of flight control cable tension between

50 flight hours and 200 flight hours after installing new cable(s) due to cable stretch and/

or thermal variances within aircraft operating area.

E. Approval:

FAA Approved for Engineering Design.

F. Manpower:

Individual aircraft may vary. It is recommended that operators obtain an estimate from

their nearest M7 Aerospace authorized Service Facility/Maintenance Department.
Issued: June 27, 2011 226-27-072

Page 2 of 8

SERVICE BULLETIN

SA226 SERIES

G. Material – Cost and Availability:

Contact your nearest M7 Aerospace authorized Service Facility/Maintenance Department. It is recommended that operators notify M7 Aerospace/Distributor 45 days prior

to new cable(s) being required to accommodate manufacturing schedules.

H. Tooling – Price and Availability:

Kit, Swage, Control Cable P/N AT520JK

Kit, Pull Test, Control Cable P/N AT520CTK

Contact M7 Aerospace for price and availability.

I. Weight and Balance:

Weight and Balance unaffected.

J. References:

Swearingen Aviation Corporation drawing 27-13090, Rev B and EO's C-1, C-2A,

C-3, C-4, C-5, C-6, and C-7 (or latest FAA approved revision).

Swearingen Aviation Corporation drawing 27-13150, Rev A (or latest FAA

approved revision).

Swearingen Aviation Corporation drawing 27-13219, Rev IR and EO's A-1 and

A-2 (or latest FAA approved revision).

Swearingen Aviation Corporation drawing 27-13216, Rev IR and EO's A-1 and

A-2A (or latest FAA approved revision).

Swearingen Aviation Corporation drawing 27-13300, Rev IR and EO's A-1, A-2,

A-3, A-4, and A-5 (or latest FAA approved revision).

Swearingen Aviation Corporation drawing 27-13242, Rev IR and EO's A-1 A-2,

A-3, A-4, A-5, A-6, A-7, and A-8 (or latest FAA approved revision).

Swearingen Aviation Corporation drawing 27-13233, Rev IR and EO A-1 (or latest

FAA approved revision).

Swearingen Aviation Corporation drawing 27-13181, Rev IR and EO A-1 (or latest

FAA approved revision).

NOTE: References are for manufacturer’s use only.

K. Other Publications Affected:

SA226 Maintenance Manual.

SA226 Illustrated Parts Catalog.
Issued: June 27, 2011 226-27-072

Page 3 of 8

SERVICE BULLETIN

SA226 SERIES

2. ACCOMPLISHMENT INSTRUCTIONS

A. Disconnect electrical power from the aircraft. Turn off main batteries. Disconnect

GPU. Tag out circuit breakers and battery switches to prevent injury to personnel or

damage to the aircraft.

B. Time limits have been revised for control cables installed in aircraft listed in the

effectivity section of this service bulletin. For the specific cables identified in step

2.C., 2.D., and 2.E., the following Table 1 intervals must be followed.

TABLE 1

A e ction Required I l nitial Compliance Tim Repetitive Interva

For cables less than or equal to

3500 hours TIS, replace cables.

By 3500 hours TIS or 150 hours

TIS from the effective date of this

service bulletin, whichever occurs

later.

Every 3500 hours TIS

thereafter.

For cables less than or equal to

5000 hours TIS, but greater than

3500 hours TIS, replace cables.

Within 150 hours TIS from the

effective date of this service

bulletin.

Every 3500 hours TIS

thereafter.

For cables greater than 5000

hours TIS, replace cables.

Within 50 hours TIS from the

effective date of this service

bulletin.

Every 3500 hours TIS

thereafter.

For cables greater than 6000

hours TIS,

(i) inspect cables, replace if

deficiencies are found.

(ii) Replace cables.

(i) Within 10 hours TIS from the

effective date of this service

bulletin; replace prior to further

flight if deficiencies are found.

(ii) Within 50 hours TIS from the

effective date of this service

bulletin.

(i) None

(ii) Every 3500 hours TIS

thereafter.

Check flight control cable tension

per SA226 Maintenance Manual,

Chapter 27-00-00.

Between 50 and 200 hours after

installing any new control cable.

None.
Issued: June 27, 2011 226-27-072

Page 4 of 8

SERVICE BULLETIN

SA226 SERIES

All other flight control cables not affected by this service bulletin are to be

periodically inspected or replaced in accordance with AD87-02-02.

Ten (10) hour inspection procedure for cables greater than 6,000 hours:

(1) Release tension on each cable.

(2) Pass a cloth along the entire length of each cable to clean the cable for visual

inspection and to detect broken wires.Visual inspect the entire cable length for

broken wires and general condition. Rotate the cable 180° where the cable

contacts any pulley, fairlead or pressure seal. Birdcage cable (slightly untwist),

and visually inspect for wear, broken wires and for general condition 24 inches

either side of contact area when the control cables are in the neutral position.

(3) Prior to further flight replace, with a new cable, any cable found to have any one of the following conditions:

(a) More than three (3) broken wires within any one-foot section of the cable (any wire

worn more than one half of its diameter is considered broken), or

(b) More than one (1) one-foot section with broken wires, or

(c) Cables whose total number of broken wires exceeds the total number of feet in

length of that cable, or

(d) More than six (6) wires worn not more than one-half of the wire diameter in any

one-inch length of cable.

(4) In cases where discrepant cables have been found, prior to further flight, inspect

the condition of the associated fairleads / pressure seals or pulleys in accordance

with SA226 Maintenance Manual, Chapter 27-00-00. Replace any unserviceable

components as required.

(5) Prior to returning the airplane to service, reset cable tensions, rerig primary flight

control systems, reaasemble the airplane, and verify proper control systems

operation in accordance with SA226 Maintenance Manual, Chapter 27-00-00.

Make appropriate maintenance record entry per step 2.I.

C. Replace flight control cables as follows for aircraft serial numbers. T265, T267,

T(B)348 (Camera Mod, Fwd, ~ FS 116 to FS 261):

NOTE: Refer to general instructions on removal/installation of flight control cables per

SA226 Maintenance manual chapter 27-00-00. The following steps refer to

figure numbers which are found in the respective maintenance manual

chapters.

NOTE: Refer to Kit Drawing 27K70004 for further installation details.
Issued: June 27, 2011 226-27-072

Page 5 of 8

SERVICE BULLETIN

SA226 SERIES

(1) Remove and replace Pilot and/or Copilot aileron cables 3 / 4 (Ref. Figures 202

and 203) between FS 98.56 (Control Wheel) and FS 225.78 (Aileron Interconnect

Bellcrank) per SA226 Maintenance Manual Chapter 27-10-01.

(2) Remove and replace Pilot and/or Copilot rudder/aileron interconnect cable 2

(Ref. Figure 1B) between FS 225.78 (from spring assembly aft attach point) and

FS 243.19 (rudder trim tab cable connecting link) per SA226 Maintenance

Manual Chapter 27-20-01.

(3) Remove and replace Pilot and/or Copilot aileron trim tab cable (Ref. Figure 1)

between FS 126.06 (Pedestal) and ~ FS 216 (Wing Rear Spar) per SA226

Maintenance Manual Chapter 27-10-04.

(4) Remove and replace Pilot and/or Copilot rudder cables (Ref. Figure 1) per

SA226 Maintenance Manual Chapter 27-20-01.

(5) Remove and replace rudder trim tab cable (Ref. Figure 1) per SA226 Maintenance Manual Chapter 27-20-05.

(6) Remove and replace Pilot and/or Copilot elevator cable (Ref. Figure 1) per

SA226 Maintenance Manual Chapter 27-30-01.

NOTE: Follow procedures in SA226 Maintenance Manual chapter 20-10-10 for

turnbuckle safety springs (if installed) or turnbuckle safety wiring.

(7) Set rigging tension for SA226-T aircraft per SA226 Maintenance Manual chapter

27-00-00, Figure 207.

D. Replace flight control cables as follows for aircraft serial numbers. AT071, AT072,

and AT073 (Camera Mod, Fwd, ~ F.S. 174 to 455):

NOTE: Refer to general instructions on removal/installation of flight control cables per

SA226 Maintenance manual chapter 27-00-00. The following steps refer to

figure numbers which are found in the respective maintenance manual

chapters.

NOTE: Refer to Kit Drawing 27K70004 for further installation details.

(1) Remove and replace Pilot and/or Copilot aileron cables 3 / 4 between FS 174.06

(Control Wheel) and FS 332.27 (Aileron Interconnect bellcrank) per SA226

Maintenance Manual Chapter 27-10-01.

(2) Remove and replace Pilot and/or Copilot rudder/aileron interconnect cable 2

(Ref. Figure 1B) between FS 324.77 (from spring assembly aft attach point) and

FS 347.27 (rudder trim tab cable connecting link) per SA226 Maintenance

Manual Chapter 27-20-01.
Issued: June 27, 2011 226-27-072

Page 6 of 8

SERVICE BULLETIN

SA226 SERIES

(3) Remove and replace Pilot and/or Copilot aileron trim tab cable (Ref. Figure 1) per

SA226 Maintenance Manual Chapter 27-10-04.

(4) Remove and replace Pilot and/or Copilot rudder cables (Ref. Figure 1) per

SA226 Maintenance Manual Chapter 27-20-01.

(5) Remove and replace rudder trim tab cable (Ref. Figure 1) per SA226 Maintenance Manual Chapter 27-20-05.

(6) Remove and replace Pilot and/or Copilot elevator cables 1 and 2 (Ref. Figure 1)

per SA226 Maintenance Manual Chapter 27-30-01.

NOTE: Follow procedures in SA226 Maintenance Manual chapter 20-10-10 for

turnbuckle safety springs (if installed) or turnbuckle safety wiring.

(7) Set rigging tension for SA226-AT aircraft per SA226 Maintenance Manual

chapter 27-00-00, Figure 209.

E. Replace flight control cables as follows for aircraft serial number TC277 (Camera

Mod, Aft, ~ F.S. 347 to 455):

NOTE: Refer to general instructions on removal/installation of flight control cables per

SA226 Maintenance manual chapter 27-00-00. The following steps refer to

figure numbers which are found in the respective maintenance manual

chapters.

NOTE: Refer to Kit Drawing 27K70004 for further installation details.

(1) Remove and replace Pilot and/or Copilot rudder cable 3 (Ref. Figure 1) per

SA226 Maintenance Manual Chapter 27-20-01.

(2) Remove and replace rudder trim tab cable (Ref. Figure 1) per SA226 Maintenance Manual Chapter 27-20-05.

(3) Remove and replace Pilot and/or Copilot elevator cable 1 per SA226 Maintenance Manual Chapter 27-30-01.

NOTE: Follow procedures in SA226 Maintenance Manual chapter 20-10-10 for

turnbuckle safety springs (if installed) or turnbuckle safety wiring.

(4) Set rigging tension for SA226-TC aircraft per SA226 Maintenance Manual

chapter 27-00-00, Figure 209.

F. Remove tags from battery switches and circuit breakers pulled in step 2.A. and

reset. Reconnect GPU to aircraft.

G. Perform Adjustment/Test of primary flight controls per applicable sections of SA226

Maintenance Manual, chapter 27.
Issued: June 27, 2011 226-27-072

Page 7 of 8

SERVICE BULLETIN

SA226 SERIES

H. Return aircraft to serviceable condition.

I. Complete aircraft records according to 14 CFR 43.9.

J. Complete and mail Service Bulletin compliance form to M7 Aerospace Technical

Publications.

3. MATERIAL LISTING

For Aircraft Serial Numbers T265, T267, and T(B)348.

NEW P/N QTY. NOMENCLATURE OLD P/N DISPOSITION

27-13181-001SB 1 Aileron Control Cable, 27-13181-001 Scrap

Cable 3 / 4, Pilot

27-13181-007SB 1 Aileron Control Cable, 27-13181-007 Scrap

Cable 3 / 4, Copilot

27-13181-015SB 1 Aileron Trim Tab 27-13181-015 Scrap

Control Cable

27-13181-003SB 2 Rudder Control Cable 27-13181-003 Scrap

27-13181-009SB 2 Rudder/Aileron 27-13181-009 Scrap

Interconnect Cable 2

27-13181-019SB 1 Rudder Trim Tab 27-13181-019 Scrap

Control Cable

27-13181-005SB 1 Elevator Control 27-13181-005 Scrap

Cable

27-13181-011SB 1 Elevator Control 27-13181-011 Scrap

Cable

27K70004 1 Kit Drawing None None

For Aircraft Serial Numbers AT071, AT072, and AT073.

NEW P/N QTY. NOMENCLATURE OLD P/N DISPOSITION

27-13233-015SB 2 Aileron Control Cables 27-13233-015 Scrap

3 / 4

27-13233-007SB 1 Aileron Trim Tab 27-13233-007 Scrap

Control Cable

27-13233-077SB 2 Rudder Control Cable 27-13233-077 Scrap

27-13233-009SB 1 Rudder Trim Tab 27-13233-009 Scrap

Control Cable

27-13233-011SB 1 Elevator Control 27-13233-011 Scrap

Cables 1 and 2, LH

27-13233-013SB 1 Elevator Control 27-13233-013 Scrap

Cables 1 and 2, RH
Issued: June 27, 2011 226-27-072

Page 8 of 8

SERVICE BULLETIN

SA226 SERIES

For Aircraft Serial Numbers AT071, AT072, and AT073 (Continued).

NEW P/N QTY. NOMENCLATURE OLD P/N DISPOSITION

27K70004 1 Kit Drawing None None

For Aircraft Serial Numbers TC277.

NEW P/N QTY. NOMENCLATURE OLD P/N DISPOSITION

27-13216-009SB 2 Elevator Control Cable 27-13216-009 Scrap

27-13216-007SB 2 Rudder Control Cable 27-13216-007 Scrap

27-13216-005SB 1 Rudder Trim Tab 27-13216-005 Scrap

Control Cable

27K70004 1 Kit Drawing None None